EP0683312A1 - Fester Brennstoffblock eines Hybridtriebwerks - Google Patents

Fester Brennstoffblock eines Hybridtriebwerks Download PDF

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Publication number
EP0683312A1
EP0683312A1 EP94303354A EP94303354A EP0683312A1 EP 0683312 A1 EP0683312 A1 EP 0683312A1 EP 94303354 A EP94303354 A EP 94303354A EP 94303354 A EP94303354 A EP 94303354A EP 0683312 A1 EP0683312 A1 EP 0683312A1
Authority
EP
European Patent Office
Prior art keywords
grain
fuel
rocket
fuel grain
solid fuel
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP94303354A
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English (en)
French (fr)
Other versions
EP0683312B1 (de
Inventor
Bevin C. Mckinney
Roy J. Kniffen, Jr.
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
American Rocket Co
Original Assignee
American Rocket Co
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Priority to US07/986,087 priority Critical patent/US5339625A/en
Application filed by American Rocket Co filed Critical American Rocket Co
Priority to DE69417878T priority patent/DE69417878D1/de
Priority to EP94303354A priority patent/EP0683312B1/de
Publication of EP0683312A1 publication Critical patent/EP0683312A1/de
Application granted granted Critical
Publication of EP0683312B1 publication Critical patent/EP0683312B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • C—CHEMISTRY; METALLURGY
    • C06—EXPLOSIVES; MATCHES
    • C06D—MEANS FOR GENERATING SMOKE OR MIST; GAS-ATTACK COMPOSITIONS; GENERATION OF GAS FOR BLASTING OR PROPULSION (CHEMICAL PART)
    • C06D5/00—Generation of pressure gas, e.g. for blasting cartridges, starting cartridges, rockets
    • C06D5/10—Generation of pressure gas, e.g. for blasting cartridges, starting cartridges, rockets by reaction of solids with liquids
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
    • F02K9/10—Shape or structure of solid propellant charges
    • F02K9/14—Shape or structure of solid propellant charges made from sheet-like materials, e.g. of carpet-roll type, of layered structure
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
    • F02K9/32—Constructional parts; Details not otherwise provided for
    • F02K9/36—Propellant charge supports
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/72—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid and solid propellants, i.e. hybrid rocket-engine plants

Definitions

  • the present invention generally relates to the art of rocket propulsion systems, and more specifically to an improved configuration for a solid fuel grain component of a hybrid rocket motor.
  • a hybrid rocket engine or motor is a cross between a solid propellant rocket motor and a liquid propellant rocket motor.
  • a hybrid utilizes a fluid oxidizer to burn a solid fuel element.
  • the hybrid rocket propellant can be ignited by an igniter such as an electrically generated spark, or by initial injection of an ignition fluid which exothermically reacts with the liquid oxidizer.
  • a "reverse" hybrid applies a combustible liquid fuel to a solid oxidizer. This application relates to the solid fuel/fluid oxidizer form of hybrid which, generally, is well known. Many examples of various hybrid rocket configurations appear, for example, in the patent literature. Representative are U.S. Patent Nos.
  • Some of the more well known advantages of a hybrid rocket motor over a purely solid or purely liquid fuel rocket motor are: (1) the complete separation of fuel from the principal oxidizer, thus eliminating the potential for uncontrolled mixing; (2) the capability of optimizing the combination of propellant ingredients regardless of whether these are solid or liquid, and (3) the capability of easily stopping and restarting the motor.
  • the engine In addition to its on-off capability, the engine is easily throttleable since there is only one liquid component.
  • the solid fuel component need not contain any oxidizer, it is easily mass produced under less hazardous conditions and at less cost.
  • a conventional hybrid rocket motor includes a hollow housing or combustion chamber in which an elongated solid fuel component, or "grain", is secured.
  • the solid fuel grain may have a "wagon wheel” cross sectional shape as disclosed in the above-identified U.S. Patent No. 5,119,627, with a central hollow hub, an outer rim, and a plurality of spokes joining the hub to the rim.
  • the wedge-shaped spaces between the spokes known as combustion "ports" extend the axial length of the grain, thereby allowing combustion gas to flow through the grain.
  • the liquid or gaseous oxidizer is provided in a tank or container mounted forward of the fuel grain, and is caused to flow through the fuel grain passages. Ignition causes combustion of the fuel-oxidizer mixture at the exposed surfaces of the fuel grain, resulting in the generation of thrust as the high pressure combustion products are discharged through the rocket nozzle.
  • a significant problem inherent in conventional hybrid rocket motor design is that it is difficult to burn all of the solid fuel grain in a controlled manner. When it is attempted to burn the entire fuel grain, a point is reached where a central unburned portion separates from the main body from the grain, and is moved by the combustion gas flow into the nozzle area, causing a major reduction in thrust, and potentially significant damage to the nozzle and/or rocket. This may be avoided by burning the fuel grain only down to a point at which the undesirable separation will not occur. This is not a completely satisfactory solution, however, since the remaining portion of the fuel grain, and hence also precious space and weight in the rocket motor, is wasted.
  • the disadvantage of the wagon wheel design is that because of the slow burning rate of the fuel, the webs become very thin during the last portion of the burn and again, subject to separation. It has been attempted to reinforce the wagon wheel fuel grain by incorporating solid stiffening sheets in the spoke or web portions of the grain. This too has not proven satisfactory since the fuel grain tends to separate from the solid sheets during burning.
  • the present invention retains the overall benefits of the wagon wheel fuel grain design but at the same time overcomes the above described disadvantages by maintaining the integrity of the fuel grain particularly during the last portion of the burn through the incorporation of fuel strengthening agents and/or mechanical retention devices.
  • the hybrid fuel formulation is a modified elastomeric polyurethane reaction product based on a liquid hydroxyl-terminated homopolymer of butadiene.
  • this invention in one exemplary embodiment relates to the addition of a reinforcing agent which improves the physical properties of the polybutadiene elastomer fuel grain.
  • a reinforcing agent which improves the physical properties of the polybutadiene elastomer fuel grain.
  • a short chain diol such as VoranolTM increases the tensile and tear strength of the grain by 50%. By so strengthening the grain, separation of the grain during the last portion of the burn is minimized.
  • mechanical web or sheet stiffeners are provided in the form of a core configuration about which the fuel grain is cast.
  • the stiffeners are in the form of a tetrahexagonal or honeycomb-like truss structure in sheet form.
  • the fuel is cast directly into the motor casing but, in order to achieve the wagon wheel shape, a series of port molds and associated center mold must be inserted in the casing prior to casting.
  • the stiffeners are centered within the fuel receiving cavities between the port molds.
  • the stiffener structure mechanically traps and adheres to the fuel, and thus becomes an integral part of the fuel grain geometry.
  • the mold parts are removed from the motor casing, leaving the reinforced wagon wheel fuel grain in place within the casing.
  • a solid fuel grain component for a hybrid rocket motor comprising:
  • the invention relates to a solid fuel grain component for a hybrid rocket motor comprising:
  • the invention relates to a hybrid rocket comprising a casing, a hybrid fuel rocket motor located within the casing, and a nozzle fixed at a rearward end of the casing;
  • the motor including a solid fuel grain component having a substantially wagon wheel cross-sectional shape including a hub and a plurality of radial spoke sections, the fuel grain including:
  • a hybrid propellant rocket 10 includes generally an outer casing or shell 12 mounting a payload 14 carried in the forward nose portion of the rocket. Propulsion for the rocket 10 is provided by a hybrid rocket motor propulsion system indicated generally by numeral 16.
  • the aft section 18 of the rocket casing 12 also comprises the motor casing which constitutes the combustion chamber for the rocket.
  • the motor casing 18 is generally cylindrical in shape and has a rearward end bell 18a and a forward end bell 18b which are bolted and bonded or otherwise suitably attached within opposite ends of the casing. Both end bells 18a, 18b are lined with fuel, thereby enhancing the efficiency of the motor 16.
  • the aft end bell 18a is for mixing the unburned combustion gases and the forward end bell 18b is an oxidizer mixing chamber.
  • Nozzle 20 is fitted to the rear end bell 18a for rearward discharge of combustion gases from the casing 18 to generate thrust.
  • a generally cylindrical solid fuel grain component 22 is supported within the casing 18. Front and rear combustion chambers 24 and 26 are provided forwardly and rearwardly of the grain 22 as defined by the forward end bell 18b and rearward end bell 18a.
  • the hybrid motor is supplied with liquid or gaseous oxidizer from a tank 28 located forwardly of the motor casing 18.
  • the fluid propellant component for example, liquid oxygen (LOx)
  • LOx liquid oxygen
  • injector 30 a non-flammable pressurizing gas such as helium is used to pressurize the LOx within the tank 28. This is accomplished with a pressurization system 32 located between the liquid propellant tank 28 and the payload 14.
  • the fuel grain 22 is illustrated in cross-section to show more clearly the improvements of this invention.
  • the fuel grain 22 has a wagon wheel cross sectional shape which includes a central hub 34, a radially outer rim 36 and a plurality of radially extending spokes 38 connecting the hub 34 to the rim 36.
  • This arrangement provides a hollow center port 40 and a plurality of wedge-shaped port passages 42.
  • the hybrid fuel grain 22 is essentially a modified elastomeric polyurethane reaction product based on a liquid, hydroxyl-terminated homopolymer of butadiene. Carbon powder is added to the mix to block infrared radiation through the fuel during combustion.
  • the nominal formulation for this fuel is as follows: R-45HT (polyurethane resin) Atochem Inc. 100. parts by weight Isonate 2143L (isocyanate curing agent) The Dow Chemical Co. 12.5 parts by weight Darco GFP (carbon powder) American Norit Co. Inc. 2.0 parts by weight
  • a reinforcing agent is added which improves the physical properties of the polybutadiene elastomer.
  • an auxiliary polyol e.g., a short chain diol such as Voranol TM is added to the fuel mixture which improves the tensile and tear strength of the fuel grain by 50%. While it is acknowledged that a short chain diol such as VoranolTM is known to increase the strength of rubber compounds including polybutadiene, it has not to applicants' knowledge been utilized previously to increase the strength of polybutadiene in the context of a hybrid rocket motor.
  • a short chain diol such as VoranolTM is added to the fuel grain so as to comprise approximately 3.0% of the total fuel by weight.
  • other chemical compositions may be suitable for use as reinforcing agents.
  • other additives may be included in the fuel mixture such as, for example, extenders and combustion enhancers.
  • the fuel grain 22 is reinforced by a series of open-lattice type reinforcers or stiffeners 44, with one such stiffener located centrally of each radial spoke 38 of the wagon wheel fuel grain 22.
  • Each stiffener structure extends along substantially the entire axial length of the grain 22, and radially from approximately the center port or hub 40 of the grain to the radially outer periphery or rim 36.
  • an inverted V-shaped "sliver" 46 extending axially along a portion of the length of each stiffener, for a purpose described below.
  • the slivers 46 extend only along the aft section of the fuel grain, preferably along about the aft 1/3 of the grain.
  • the stiffeners 44 are constructed of an injection molded tetrahexagonal truss structure available from Tetrahex, Inc. of Camarillo, CA under the name "Tetraweb".
  • Tetrahex, Inc. of Camarillo, CA under the name "Tetraweb”.
  • This material also disclosed in U.S. Patent No. 4,967,533 (the entirety of which is incorporated herein by reference) is shown in some detail in Figure 4 and includes an arrangement where the apices of the individual tetrahedrons 48 of the structure are truncated and made hollow as shown at 50. The specific configuration of the structure is explained in greater detail in the '533 patent.
  • stiffeners 44 becomes an integral part of the fuel grain geometry in the sense that, during manufacture of the fuel grain, a stiffener 44 and foam sliver 46 are centered within each cavity (to receive fuel in the casting process which will form a spoke 38) between adjacent port molds 52, 54, as best seen in Figures 5 and 6. It will be appreciated that sufficient port molds are inserted in the casing 18 and arranged in an annular array so as to produce the desired wagon wheel design.
  • the stiffeners 44 are inserted into the cavities and each is centered within its respective cavity by a pair of pins 56, 58. These pins are received in sockets 60, 62, respectively, (molded into the stiffener 44) and extend laterally away from either side of the stiffener 44 to engage the port molds 52, 54.
  • the port mold elements and the core mold are removed, leaving the wagon-wheel shaped fuel grain in place within the casing, with the fuel material interlocked within the tetrahexagonal openings in the web stiffeners 44, as best seen in Figure 5.
  • other stiffener structures may be employed so long as the stiffener structure causes the fuel to interlock with the stiffener during casting of the fuel.
  • the center port 40 may be plugged (with material cast into the port) in some instances so that all of the LOx flows through the port passages 42. For other applications, the center port 40 may be left open.
  • the stiffeners 44 are partially consumed, but maintain fuel grain integrity during the last portion of the burn.
  • centering pins 56, 58 are fabricated out of a material having a similar burning rate to the solid fuel grain 22 and are consumed along with the fuel during motor operation.
  • the foam slivers 46 are composed of urethane foam or any plastic foam with good fuel characteristics.
  • the burning rate of the foam is tailored by varying the density of the foam.
  • the foam slivers 46 serve several functions including:

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Organic Chemistry (AREA)
  • Solid Fuels And Fuel-Associated Substances (AREA)
EP94303354A 1992-12-04 1994-05-10 Fester Brennstoffblock eines Hybridtriebwerks Expired - Lifetime EP0683312B1 (de)

Priority Applications (3)

Application Number Priority Date Filing Date Title
US07/986,087 US5339625A (en) 1992-12-04 1992-12-04 Hybrid rocket motor solid fuel grain
DE69417878T DE69417878D1 (de) 1994-05-10 1994-05-10 Fester Brennstoffblock eines Hybridtriebwerks
EP94303354A EP0683312B1 (de) 1992-12-04 1994-05-10 Fester Brennstoffblock eines Hybridtriebwerks

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US07/986,087 US5339625A (en) 1992-12-04 1992-12-04 Hybrid rocket motor solid fuel grain
EP94303354A EP0683312B1 (de) 1992-12-04 1994-05-10 Fester Brennstoffblock eines Hybridtriebwerks

Publications (2)

Publication Number Publication Date
EP0683312A1 true EP0683312A1 (de) 1995-11-22
EP0683312B1 EP0683312B1 (de) 1999-04-14

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EP94303354A Expired - Lifetime EP0683312B1 (de) 1992-12-04 1994-05-10 Fester Brennstoffblock eines Hybridtriebwerks

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EP (1) EP0683312B1 (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102017100058B4 (de) 2016-02-22 2024-06-20 Bayern-Chemie Gesellschaft Für Flugchemische Antriebe Mbh Vorrichtung zur Stabilisierung einer Treibstoffanordnung unter Formung von Abströmkanälen

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US5767973A (en) * 1996-02-07 1998-06-16 Simmons Machine Tool Corporation Wheelset sensing system
US5718113A (en) * 1994-12-28 1998-02-17 Hayes; Michael D. Fuel strip
US5794435A (en) * 1996-02-07 1998-08-18 Lockhhed Martin Corporation Stable-combustion oxidizer vaporizer for hybrid rockets
US5765361A (en) * 1996-08-23 1998-06-16 Jones; Herbert Stephen Hybrid-LO2-LH2 low cost launch vehicle
US7503165B2 (en) * 2004-09-29 2009-03-17 Spacedev, Inc. Hybrid propulsion system
US7404288B2 (en) * 2004-10-28 2008-07-29 Spacedev, Inc. High propulsion mass fraction hybrid propellant system
US8707676B2 (en) * 2008-02-28 2014-04-29 The Aerospace Corporation Radial flow rapid prototyping rocket motors
US8601790B2 (en) * 2008-02-28 2013-12-10 The Aerospace Corporation Buried radial flow rapid prototyping rocket motors
US8225507B2 (en) * 2008-02-28 2012-07-24 The Aerospace Corporation Stereolithographic rocket motor manufacturing method
JP5484796B2 (ja) * 2009-06-19 2014-05-07 三菱重工業株式会社 ハイブリッドロケットエンジン
US9429104B2 (en) 2011-08-01 2016-08-30 The Aerospace Corporation Systems and methods for casting hybrid rocket motor fuel grains
US9038368B2 (en) * 2011-08-01 2015-05-26 The Aerospace Corporation Systems, methods, and apparatus for providing a multi-fuel hybrid rocket motor
RU2657077C1 (ru) * 2016-03-31 2018-06-08 Акционерное общество "Федеральный научно-производственный центр "Алтай" Способ изготовления скрепленного с корпусом заряда смесевого ракетного твердого топлива формованием свободным литьем
CN109236501A (zh) * 2018-10-18 2019-01-18 翰贝摩尔表面技术（江苏）有限公司 一种运载火箭喷射装置的挡药板
CN114893326B (zh) * 2022-06-14 2022-11-01 中国科学院力学研究所 一种固液火箭发动机氧燃比偏移控制方法

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102017100058B4 (de) 2016-02-22 2024-06-20 Bayern-Chemie Gesellschaft Für Flugchemische Antriebe Mbh Vorrichtung zur Stabilisierung einer Treibstoffanordnung unter Formung von Abströmkanälen

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EP0683312B1 (de) 1999-04-14
US5339625A (en) 1994-08-23

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